| Liquid Rocket Propulsion - Evolution and Advancements: Rocket-Based Combined Cycle | 25 JUN 1999 | 49 pages |
| Authors: Ray Moszee;AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST |
 | This document on Rocket-Based Combined Cycles discusses history of RBCC, integrated performance analysis, current activities and future prospects. |
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| Development and Test of an Advanced Expander Combustor | 24 JUN 1999 | 13 pages |
| Authors: T. Jennings;S. Fentress;S. Peery;A. Minick;PRATT AND WHITNEY WEST PALM BEACH FL LIQUID SPACE PROPULSION |
| This paper discusses development and test of an advanced expander combustion chamber for a 50,000 pound (222.4 kN) thrust Upper Stage Expander Cycle Engine. The chamber is being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Propulsion Technology (IHPRPT) program. The Advanced Expander Combustor is designed to provide increased heat pick-up to ... |
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| Development Status of a 50k LOX/Hydrogen Upper Stage Demonstrator | 24 JUN 1999 | 12 pages |
| Authors: R. Long;R. Grabowski;A. Minick;S. Peery;R. Branam;PRATT AND WHITNEY WEST PALM BEACH FL |
| This paper discusses design and systems integration status of a 50, 000 pound (222.4 kN) thrust Oxygen/Hydrogen Upper Stage Engine Demonstrator (USD) being created by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Propulsion Technology (IHPRPT) program. The objective of this program is to integrate advanced technology components into an expander cycle engine configuration ... |
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| Fractal Geometry and Growth Rate Changes of Cryogenic Jets Near the Critical Point | 14 JUN 1999 | 16 pages |
| Authors: B. Chehroudi;D. Talley;E. Coy;AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST |
| Injection of several pure fluids into a chamber with different ambient gases under supercritical temperature but sub- to supercritical condition based on the injectant thermodynamic critical conditions resulted in the following: the jet exhibits classical liquid-like jet second wind-induced type breakup until chamber pressure reaches near the critical point of the jet substance beyond which gas-like visual behavior is observed and no drops are found. For the first time, these ... |
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| Recent ASI Progress in Pulse Detonation Rocket Engine (PDRE) Hardware Development | 11 JUN 1999 | 18 pages |
| Authors: D. C. Mueller;T. E. Bratkovich;K. Lupkes;S. Henderson;J. T. Williams;ADROIT SYSTEMS INC ALEXANDRIA VA |
| This paper presents a brief overview of Adroit Systems, Inc. (ASI) experimental Pulse Detonation Rocket Engine (PDRE) development efforts and accompanying numerical modeling efforts. Test results for thirty-second firings of a H2/O2 fueled combustor at firing frequencies of up to 95 Hz are presented for a range of propellant mixture ratios. These experimental results were then used to validate a single-combustor computational model. The necessity of elevated operating pressure to ... |
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| Laboratory Characterization of High Energy Materials | 10 JUN 1999 | 14 pages |
| Authors: A. J. Brand;T. W. Hawkins;M. B. McKay;I. M. Ismail;AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV |
| AFN has demonstrated acceptable properties to further propellant development: displayed good stability (thermal, friction, impact and detonability), low melt point is suitable for monopropellant applications, and extremely low toxic vapor concentrations. AFN based propellant has been evaluated to indicate additional development is warranted: high performance demonstrated in thruster test bed, acceptable safety properties and low toxic vapor concentrations. |
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| Injector and Combustion Chamber Advances Demonstrated on the Thrust Cell Technologies Program | 08 JUN 1999 | 13 pages |
| Authors: Brian Wherley;Don Ulmer;Scott Claflin;BOEING NORTH AMERICAN INC CANOGA PARK CA ROCKETDYNE DIV |
| This report covers achievements on the Thrust Cell Technologies Program (TCTP) from 1 September 1992 to 3 December 1998. The Thrust Cell Technologies Program was initiated by the Air Force Research Lab (AFRL) to: (1) develop the materials and fabrication technologies needed to produce reliable, high-performance liquid oxygen/liquid hydrogen (LOX/LH2) thrust cells for advanced upper stage engines and multi-cell booster applications, and (2) quantify the performance of modular thrust cells ... |
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| Covering Achievements of the US Air Force Thrust Cell Technologies Program and Light Weight Thrust Chamber Assembly Program | JUN 1999 | |
| Authors: Bruce Farner;Brian Wherley;Don Ulmer;Scott Claflin;Suzanne Ferrell;BOEING NORTH AMERICAN INC CANOGA PARK CA ROCKETDYNE DIV |
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| Combustion Enhancements in Advanced Liquid Rocket Engines | 17 MAY 1999 | 43 pages |
| Authors: Robert J. Santoro;PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING |
| A series of liquid jet experiments, utilizing water as the working fluid and an optically accessible orifice with a LID ratio of 2.5, were performed using laser velocimetry to map the velocity profile at several locations within the orifice. Additional measurements were also made downstream of the orifice exit in the free jet. Finally, measurements were made for a 300 angled orifice to more closely simulate actual injector conditions. The ... |
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| Anatomical Changes of a Cryogenic Jet in Transition to the Thermodynamic Supercritical Condition | 04 MAY 1999 | 8 pages |
| Authors: B. Chehroudi;D. Talley;E. Coy;AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST |
| The high pressure supercritical facility at the Air Force Research Laboratory at Edwards Air Force Base is used to investigate the effects of chamber pressure (density) ranging from the thermodynamic subcritical to supercritical values at a supercritical chamber temperature. At subcritical pressures, the jets exhibit wave-like structures that amplify downstream and eventually break up into irregularly shaped small entities. The formation of many droplets is seen at higher pressures, resembling ... |
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| Basic Research in Liquid Rocket Combustion at the Air Force Research Laboratory | MAY 1999 | 44 pages |
| Authors: Doug Talley;AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV |
| Viewgraph slides for presentation on Air Force research on liquid rocket combustion given at an international workshop on research status and perspectives in liquid rocket combustion chamber flow dynamics. |
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| Modeling Primary Atomization Processes | 01 FEB 1999 | 127 pages |
| Authors: Stephen D. Heister;PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS |
| The contributions of atomization processes to combustion instabilities in liquid rocket engines has been assessed via a series of analytic/numerical models. Simulations of high-speed injection of a viscous jet have revealed a jet "swelling" phenomenon for the first time. Modeling of F-1 fuel injectors reveals a potential instability of the fuel columns to transverse acoustic modes in injector designs which showed large instabilities. Limited ... |
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| International Workshop on Research Status of Perspectives in Liquid Rocket Chamber Dynamics | 1999 | 585 pages |
| Authors: CHITTENANGO MIDDLE SCHOOL NY |
| The Final Proceedings for International Workshop on Research Status of Perspectives in Liquid Rocket Chamber Dynamics, 27 May 1999 - 28 May 1999. This is an interdisciplinary conference. Topics will focus on liquid rocket combustion issues, including: Injection and Atomization (experimental and analysis aspects), Spray combustion in liquid rocket chambers, Experimental Methods and Diagnostics, Modeling and Analysis, Heat Transfer in combustion chamber, Liquid Rocket Combustion instability, Low Cost Technology. ... |
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| Hypersonic Missile Propulsion System | NOV 1998 | |
| Authors: Richard R. Kazmar;PRATT AND WHITNEY WEST PALM BEACH FL |
 | Pratt & Whitney is developing the technology for hypersonic components and engines. A supersonic combustion ramjet (scramjet) database was developed using hydrogen fueled propulsion systems for space access vehicles and serves as a point of departure for the current development of hydrocarbon scramjets. The Air Force Hypersonic Technology (HyTech) Program has put programs in place to develop the technologies necessary to demonstrate the operability, performance and ... |
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| Improved Performance and Durability of Liquid Propulsion Rocket Thrusters Fabricated from Triaxially Braided C-SiC Intraply Hybrid-Fiber/SiC matrix Composites | 20 OCT 1998 | |
| Authors: David E. Barland;AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST |
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| Space Shuttle On-Orbit Propulsive Capabilities | 11 SEP 1998 | 59 pages |
| Authors: Michael Davis;MARYLAND UNIV COLLEGE PARK |
| NASA's space shuttle orbiter is the premier manned spacecraft. The space shuttle orbiter allows astronauts to perform many tasks such as docking with space stations, deploying satellites, rendezvousing with and repairing the Hubble Space Telescope, etc. The shuttle orbiter would never be able to perform such tasks without its rocket propulsion system. Whenever the orbiter makes changes to its orbit, or performs orbital maneuvers, it ... |
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| Numerical Investigation of Exhaust Plume Radiative Transfer Phenomena | 15 JUL 1998 | |
| Authors: Houshang B. Ebrahimi;Alan Kawasaki;ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN |
| Accurate simulation of radiative heat-transfer effects from the rocket engine exhaust plays an important role for the proper characterization of missile base heat loads. To promote improved radiative transfer solutions, careful attention to the physical flow-field models is paramount. Use of a generalized fluid dynamic model can assist in the close approximation of the actual base heating by solving the fully coupled, two-phase, chemically reactive, ... |
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| Performance Testing of a Resistojet Thruster for Small Satellite Applications | 13 JUL 1998 | 16 pages |
| Authors: Timothy J. Lawrence;Martin Sweeting;Malcolm Paul;J. J. Sellers;J. R. LeDuc;AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV |
| Resistojets operating at low power (^lOO W) and using liquid propellants have re-emerged as attractive propulsion options for orbit-raising small satellites deployed at Space Shuttle altitudes (-2OO km). Compared to low power pulsed plasma thrusters (PPT), the resistojet produces two orders of magnitude more thrust (approximately 1.4 mN compared to 140 mN) which is required to overcome drag at solar maximum. The wet mass of both systems is approximately equal ... |
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| Design and Development of an Advanced Liquid Hydrogen Turbopump | JUL 1998 | 13 pages |
| Authors: A. Minick;S. Peery;PRATT AND WHITNEY WEST PALM BEACH FL GOVERNMENT ENGINES AND SPACE PROPULSION |
| This paper discusses design and development of an Advanced Liquid Hydrogen Turbopump for a 50,000 pound (22,6?9 kg) thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Liquid Hydrogen Turbopump is designed to provide improved system thrust to weight, decreased hardware/support ... |
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| Design and Development of an Advanced Expander Combustor | JUL 1998 | 13 pages |
| Authors: S. Peery;A. Minick;PRATT AND WHITNEY WEST PALM BEACH FL LIQUID SPACE PROPULSION |
| This paper discusses design and development of an advanced expander combustion chamber for a 50,000 pound (222.4 kN) thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Expander Combustor is designed to provide increased heat pick-up to the coolant and improved ... |
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| Design and Development of a 50K LOX/Hydrogen Upper Stage Demonstrator | JUL 1998 | 13 pages |
| Authors: S. Peery;A. Minick;PRATT AND WHITNEY WEST PALM BEACH FL |
| This paper discusses design and systems integration of a 50,000 pound (222.4 kN) thrust Oxygen/Hydrogen Upper Stage Engine Demonstrator (USD) being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Propulsion Technology (IHPRPT) program. The objective of this program is to integrate advanced technology components into an expander cycle engine configuration and demonstrate ... |
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| 1998 JANNAF Propellant Development & Characterization Subcommittee and Safety & Environmental Protection Subcommittee Joint Meeting. Volume 1 | APR 1998 | |
| Authors: James E. Cocchiaro;William L. Hufferd;Sylvia J. Gomez-Knight;CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD |
| This publication is part of a three-volume set and contains 49 technical papers that were presented at the 1998 JANNAF Propellant Development & Characterization Subcommittee (PDCS) and Safety & Environmental Protection Subcommittee (S&EPS;) Joint Meeting, held 21-24 April 1998 at NASA Johnson Space Center, Houston, Texas. Sessions jointly sponsored by both Subcommittees included propellant/Ingredient processing for pollution prevention, propellant development for pollution prevention, solid propellant ... |
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| The Effect of Manifold Cross-Flow on the Discharge Coefficient Sharp- Edged Orifices | 16 MAR 1998 | 34 pages |
| Authors: P. A. Strakey;D. G. Talley;AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST |
| The objective of this study is to determine the effect of manifold cross-flow on the discharge coefficient and cavitation characteristics of sharp- edged orifices over a wide range of flow-rates, back-pressures and cross-flow velocities. The orifice geometries studied cover a range of orifice diameters, length to diameter ratios and orifice angles characteristic of impinging element liquid rocket injectors. Experimental results for an orifice angle of 900 with respect to the ... |
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| Contributions of Shear Coaxial Injectors to Liquid Rocket Motor Combustion Instabilities | 24 OCT 97 | 12 pages |
| Authors: Michael M. Micci;PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING |
| Acoustic oscillations were induced in a subscale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data were acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. The magnetic flowmeter obtains the acoustic gas velocity by measuring the voltage induced by the ionized combustion ... |
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| High Pressure Combustion Studies Under Combustion-Driven Oscillatory Flow Conditions | 03 OCT 97 | 30 pages |
| Authors: Robert J. Santoro;PENNSYLVANIA STATE UNIV UNIVERSITY PARK |
| Rocket engines fueled by a dense propellant such as kerosene provide a number of advantages over hydrogen-fueled engines for primary stages. A major problem in the development of liquid fueled rocket engines has been the occurrence of combustion instability. The lack of a detailed understanding of how combustion instability occurs in liquid-fueled rocket engines has resulted in costly engine development programs that must be avoided in the future. The present ... |
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| JANNAF Airbreathing Propulsion Subcommittee Meeting. Volume I | OCT 1997 | |
| Authors: Ronald S. Fry;Mary T. Gannaway;CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD |
| This publication, Volume I of four volumes, contains nine unclassified/unlimited distribution papers presented at the 1997 meeting of the JANNAF Airbreathing Propulsion Subcommittee (APS) held jointly with the 34th Combustion Subcommittee (CS), and the Propulsion Systems Hazards Subcommittee (PSHS) on 27-30 October 1997 at Pratt and Whitney and the Palm Beach Gardens Marriott Hotel in West Palm Beach, Florida. Proceedings of the CS, PSHS, and APS meetings are published separately ... |
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| Application of Laser-Induced Fluorescence (LIF) to Liquid-Propellant Rocket Engine Testing | OCT 1997 | 12 pages |
| Authors: C. W. Brasier;J. A. Drakes;M. A. Simmons;SVERDRUP TECHNOLOGY INC ARNOLD AFS TN |
| Combustion exhausts present a challenging problem for researchers due to the extremely harsh environment, and nonintrusive diagnostics are often sought to provide flow property information. Laser induced fluorescence (LIF) is one technique in which a chosen flow molecule or marker is probed to yield gross flow properties, such as static temperature and flow velocities. The work presented herein describes the application of LIF to the combustion exhausts of several full-scale ... |
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| Contributions of Atomization, Vaporization and Combustion to Liquid Rocket Acoustic Energy | 15 SEP 97 | 7 pages |
| Authors: Michael M. Micci;PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING |
| Acoustic oscillations were induced in a sub-scale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data was acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. The magnetic flowmeter obtains the acoustic gas velocity by measuring the voltage induced by the ionized combustion ... |
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| Fundamental of Acoustic Instabilities in Liquid-Propellant Rockets | 14 APR 97 | 7 pages |
| Authors: F. A. Williams;CALIFORNIA UNIV SAN DIEGO LA JOLLA |
| The objective of this research was to improve understanding of the mechanisms by which flow, mixing and combustion processes are coupled to acoustic fields in liquid propellant rocket motors. Particular attention was focused on analyses of amplification mechanisms coupled with finite rate chemical reactions by use of numerical and analytical methods. A theoretical explanation of empirical correlation of instability boundaries for engine test results for LOX/RP-1 rockets was developed on ... |
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| Characterization of High-Speed Impinging Jets in a High Pressure and Temperature Environment | 20 MAR 1997 | 33 pages |
| Authors: Dimos Poulikakos;ILLINOIS UNIV AT CHICAGO CIRCLE DEPT OF MECHANICAL ENGINEERING |
| The purpose of this work is to study the dense region of two high- speed impinging jets in a temperature and pressure environment that is above atmospheric conditions. The program was terminated one year short due to the departure of the PI from the US. Nevertheless all of the goals that were set for this time period were accomplished. The measurements were performed using a double pulse, two reference beam ... |
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| Propulsion and Energy Issues for the 21st Century | MAR 97 | |
| Authors: ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE) |
| The report provides an overall projection and perspective of possible propulsion and energy technological capabilities. The 'Hypersonic Air Breathing Missile' is propelled by a liquid hydrocarbon fueled scramjet engine for Mach numbers of 5-8. An overview of merits, payoffs and critical technology development and demonstration needs of such an air breathing hypersonic missile, and Key Technology Development Requirements are presented. Technology Overviews are also presented on: turbomachinery propulsion; advanced technology ... |
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| 1996 JANNAF Propulsion Meeting, 9 December 1995-12 December 1996. Volume I | DEC 1996 | |
| Authors: Debra S. Eggleston;CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD |
| This volume, the first of three volumes, is a collection of 38 unclassified/unlimited-distribution papers which were presented at the 1996 Joint Army-Navy-NASA-Air Force (JANNAF) Propulsion Meeting (JPM), held 9-12 December 1996 at the Albuquerque Hilton Hotel in Albuquerque, New Mexico. The 1996 JPM was held jointly with the 1996 annual JANNAF meetings of the Airbreathing Propulsion, Nondestructive Evaluation, Rocket Nozzle Technology, and Structures and Mechanical Behavior Subcommittees. Specific subjects discussed ... |
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| Robust Discrete Estimation of the Space Shuttle Main Engine | JUN 96 | 70 pages |
| Authors: Jonathan A. Jensen;AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH |
| This thesis applies recently developed robust H at infinity, or game theoretic, estimation algorithms to the Space Shuttle Main Engine (SSME). The objective is to process noisy, inaccurate sensor data in order to obtain estimates of pressure in the main combustion chamber and the oxygen to fuel mixture ratio. Each of the estimators are based on discrete time, state space models of the SSME, and employ varying levels of robustness ... |
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| High Performance Ir-Re Composite | MAY 1996 | |
| Authors: Shanjin He;CERAMIC COMPOSITES INC MILLERSVILLE MD |
| A novel low temperature chemical vapor deposition (CVD) process has been developed for the co-deposition of Ir and Re. The codeposit was dense and consisted of both Re and Ir with crystallites ranging from 30 A and 1000 A in size. A reactive vapor phase was formed between 205 deg C and 220 deg C, and deposition was carried out onto quartz, graphite and rhenium substrates at between 410 deg ... |
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| Numerical Study of a Transpiration Cooled Rocket Nozzle | DEC 95 | 92 pages |
| Authors: Jay A. Landis;AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING |
| This study proved that transpiration cooling provides a better cooling scheme than regenerative cooling for long operating duration, liquid- fueled rocket engine nozzles. This proof was made on the basis of maximum wall temperature. This study compared transpiration cooling to regenerative cooling in the throat region of the Space Shuttle Main Engine Main Combustion Chamber. The study also analyzed the effects of porosity, solid thermal conductivity, and porous sphere size ... |
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| Hydrogen Peroxide for Rocket Propulsion Applications | DEC 95 | 16 pages |
| Authors: John J. Rusek;PHILLIPS LAB EDWARDS AFB CA |
| Traditionally, macroscopic metallic and ceramic screens have been used as catalysts for the controlled decomposition of hydrogen peroxide as applied to monopropellant thrusters, liquid rocket engines, and hybrid rocket systems. Catalyst activity depends on available catalytic surface area; metallic catalyst stability is generally degraded by catalyst oxidation. This paper will discuss new approaches to forming inexpensive, high surface area decomposition catalyst packs for flightweight applications. The paper will specifically discuss ... |
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| Proceedings of the JANNAF Combustion Subcommittee Meeting (32nd) and Propulsion Engineering Research Center Annual Symposium (7th) Held in Huntsville, Alabama on 23-27 October 1995. Volume 2 | 27 OCT 95 | |
| Authors: Ronald S. Fry;Mary T. Gannaway;CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD |
| This volume, the second of four volumes, is a collection of 40 unclassified/unlimited papers which were presented at the 32nd Joint Army-Navy- NASA-Air Force (JANNAF) Combustion Subcommittee Meeting in conjunction with the Propulsion Systems Hazards Subcommittee, the 22nd Exhaust Plume Technology Subcommittee, the 4th SPIRITS User Group Meeting and the Pennsylvania State University 7th Propulsion Engineering Research Center (PERC) Symposium held 23- 27 October 1995 at the NASA Marshall Space ... |
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| Dimension-Optimizing Design Method For Annular-Type Cooling Channel Of Thrust Chamber | 09 MAY 95 | 14 pages |
| Authors: Jie Chen;NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH |
| The new-generation liquid oxygen/hydrocarbon propellant liquid fuel rocket engine will use a high-pressure combustion chamber arrangement. In this case, cooling the thrust chamber becomes a key technical problem. The article presents a design scheme for the geometric-dimension optimization of annular- type regenerative cooling channels. The aim of the optimization is minimum pressure losses as coolant passes through the cooling channel. As shown in typical computations and experiments, application of this ... |
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| Optimum Design for LRE Centrifugal Pumps | 01 MAY 95 | 14 pages |
| Authors: Zuchao Zhu;Guoqian Zhang;Jiren Sun;NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH |
| We set up a mathematical model to predict low specific speed LRE centrifugal pump unit performance. Using the model in question, performance predictions were carried out for 10 types of LRE centrifugal pumps. Relative errors between experimental values and predicted values associated with efficiency and lift were all within 4%. Using the model in question, design optimization with efficiency as the target function was carried out on AM-7H and O ... |
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| Liquid Rocket Motor Combustion Stability Using Coaxial Injectors and Supercritical Droplet Combustion and Dynamics | MAY 95 | 222 pages |
| Authors: Michael M. Micci;Vigor Yang;PENNSYLVANIA STATE UNIV UNIVERSITY PARK |
| Cold flow experiments with a full-size SSME preburner shear coaxial injector element using liquid and gaseous nitrogen at pressures up to 4 MPa showed that the intact liquid core decreased in length with increasing chamber pressure up to the critical pressure, after which it increased in length. Increasing the liquid to gas mass flow rate ratio resulted in an increase in the length of the liquid core. LDV measurements showed ... |
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| The Development of Some Kinds of LRE Injectors | 28 APR 95 | 20 pages |
| Authors: Yu Yueying;NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH |
| This article introduces technical problems which appear in the development of several types of liquid rocket engine injectors and ways to solve them. At the same time, analysis was done of dual component centrifugal type injector nozzle flow amount deviations. Inquiries were made into methods of controlling flow amount deviations. A type of body interior cooling system was put forward. Option was made for the use of beveled slot drill ... |
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| Modeling Liquid Jet Atomization Processes | 19 NOV 94 | 65 pages |
| Authors: Stephen D. Heister;PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS |
| This report summarizes efforts in developing an analytic/numerical modeling capability for both steady and unsteady liquid jet atomization processes. The research involves the application of boundary element methods to model nonlinear deformation of liquid surfaces. An inviscid model has been developed to investigate dynamics of a finite-length jet which includes the presence of the orifice flow passages. In addition, a second model has been developed to simulate gas-phase interactions with ... |
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| JANNAF Combustion Subcommittee Meeting (31st) Held in Sunnyvale, California on 17-21 October 1994. Volume 1 | OCT 94 | |
| Authors: Mary T. Gannaway;CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD |
| This volume, the first of four volumes, is a collection of 32 unclassified/unlimited papers which were presented at the 31st Joint Army-Navy- NASA-Air Force (JANNAF) Combustion Subcommittee Meeting in conjunction with the Exhaust Plume Technology Subcommittee and SPIRITS User Group Meeting held 17-21 October 1994 at the Lockheed Missiles and Space Company, Sunnyvale, California. Specific subjects discussed include combustion characteristics of metallized solids in nozzles and plumes, airbreathing propulsion, advanced ... |
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| Combustion Instability Phenomena of Importance to Liquid Propellant Engines | 31 AUG 94 | 80 pages |
| Authors: Robert J. Santoro;William E. Anderson;PENNSYLVANIA STATE UNIV UNIVERSITY PARK |
| A systematic study of the atomization of impinging liquid jets was performed. Effects of jet flow condition, orifice diameter, impingement angle, pre-impingement length, fabrication procedure, and jet velocity at steady and oscillating, and atmospheric- and high-pressure ambient conditions were investigated. Measurements of sheet breakup length, drop size and velocity distribution, and the length between sheet structures and detached ligaments were made. Results of the experiments were compared to theoretical predictions. ... |
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| AFOSR Contractors Meeting in Propulsion Held in Lake Tahoe, California/ Nevada on 8-10 June 1994 | 13 JUL 94 | |
| Authors: M. A. Birkan;J. M. Tishkoff;AIR FORCE OFFICE OF SCIENTIFIC RESEARCH BOLLING AFB DC |
| Abstracts are given for research in airbreathing combustion, rocket propulsion, and diagnostics in reacting media supported by the Air Force Office of Scientific Research |
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| 155-mm Artillery Rearm Module with Liquid Propellant, Phase 1 | JUN 94 | 96 pages |
| Authors: Matthew Diehl;David Hoyt;Robert McLane;Richard Saganich;Stanley Turner;MARTIN MARIETTA ARMAMENT SYSTEMS BURLINGTON VT |
| A summary of the concept study and preliminary design for an improved 155-mm artillery rearm module (ARM) is presented. This module is to be an improvement over a 155-mm ARM designed, fabricated, and tested under previous contract (DAAA21-88-C-0161). The trade-off study effort involving liquid propellant (XM46) handling and storage concepts is discussed. The rearranging of the projectile handling magazines developed under previous contract (DAAA21-91- C-0082) is also discussed. The preliminary ... |
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| Combustion Instability Phenomena of Importance to Liquid Propellant Engines | 31 JUL 93 | 23 pages |
| Authors: Robert J. Santoro;William E. Anderson;PENNSYLVANIA STATE UNIV UNIVERSITY PARK |
| A study examining impinging liquid jets has been underway to determine physical mechanisms responsible for combustion instabilities in liquid bi-propellant rocket engines. Primary atomization has been identified as an important process. Measurements of atomization length, wave structure, and drop size and velocity distribution were made under various ambient conditions. Test parameters included geometric effects and flow effects. It was observed that pre-impingement jet conditions, specifically whether they were laminar or ... |
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| CPIA/M5 Liquid Propellant Engine Manual | 27 JUL 93 | |
| Authors: CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD |
| The F-1A is an uprated version of the F-1. It is a step-thrust bipropellant engine which uses liquid oxygen as the oxidizer and RP-1 as the fuel. The engine operates on a gas generator cycle. Nominal sea level thrust is 1,800,000 lb(sub f) with step-thrust down to 75%. The step-thrust is obtained by oxidizer flow control on the gas generator |
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| Advanced Engine Study Program | JUN 93 | 244 pages |
| Authors: A. I. Masters;D. E. Galler;T. F. Denman;R. A. Shied;J. R. Black;PRATT AND WHITNEY WEST PALM BEACH FL GOVERNMENT ENGINES AND SPACE PROPULSION |
| A design and analysis study was conducted to provide advanced engine descriptions and parametric data for space transfer vehicles. The study was based on an advanced oxygen/hydrogen engine in the 7,500 to 50,000 lbf thrust range. Emphasis was placed on defining requirements for high-performance engines capable of achieving reliable and versatile operation in a space environment. Four variations on the expander cycle were compared, and the advantages and disadvantages of ... |
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| A Method for Eliminating the Effects of Aliasing When Acquiring Interior Ballistic Data From Regenerative Liquid Propellant Guns | MAY 93 | 32 pages |
| Authors: Todd E. Rosenberger;James DeSpirito;ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD |
| Experimental investigation of interior ballistic events often requires a precise frequency spectrum analysis of data. This is particularly true in the study of high frequency pressure oscillations in the liquid propellant gun. Unfortunately, a phenomenon known as aliasing can severely bias the frequency spectrum of recorded data. In this report, aliasing is demonstrated with respect to regenerative liquid propellant gun data, and a standardized procedure is outlined to limit its ... |
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Liquid Propellant Rocket Engines
